US9631640B2 - Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing - Google Patents
Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing Download PDFInfo
- Publication number
- US9631640B2 US9631640B2 US14/363,898 US201214363898A US9631640B2 US 9631640 B2 US9631640 B2 US 9631640B2 US 201214363898 A US201214363898 A US 201214363898A US 9631640 B2 US9631640 B2 US 9631640B2
- Authority
- US
- United States
- Prior art keywords
- opposite edges
- damping
- fan casing
- damping strips
- strips
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active, expires
Links
- 238000013016 damping Methods 0.000 title claims abstract description 37
- 239000012530 fluid Substances 0.000 title description 4
- 239000007788 liquid Substances 0.000 claims abstract description 29
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 18
- 230000005484 gravity Effects 0.000 claims abstract description 16
- 239000013536 elastomeric material Substances 0.000 claims description 4
- 239000003350 kerosene Substances 0.000 description 4
- 230000001627 detrimental effect Effects 0.000 description 3
- 230000014759 maintenance of location Effects 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/002—Axial flow fans
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/663—Sound attenuation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
Definitions
- the invention relates to the mounting of an acoustic protection inside an aircraft turbomachine fan casing. More particularly, the invention is concerned with the vibration damping strips provided between the fan casing and the acoustic panels.
- the invention is applicable to any type of aircraft equipped with a fan casing, in particular turbojet engines.
- acoustic protection panels are generally assembled on the internal surface of the fan casing, about the engine axis.
- the assembly is usually performed by screwing panels to the casing.
- the selected material may be sensitive to the contact with liquids such as oil and kerosene, when dipped for a long period. This prolonged contact with such liquids can indeed cause a risk of degradation of the material and/or an efficiency loss of the damping achieved. But, in the upstream zone of the fan casing where there are the acoustic panels, oil or kerosene flows are actually possible, in case of leak.
- liquids such as oil and kerosene
- the purpose of the invention is thus to overcome at least partially the above mentioned drawbacks, relative to the systems of prior art.
- one object of the invention is to provide an acoustic protection device for a fan casing of an aircraft turbomachine, comprising an acoustic protection panel forming a ferrule sector centered on a center axis intended to be the same as the longitudinal axis of the fan casing, said device also comprising one or more vibration damping strips pressed on one side to the external surface of the acoustic protection panel and for being pressed on the other side to an internal surface of the fan casing, each damping strip having two opposites edges each having an upstream end and a downstream end spaced from each other along the direction of the center axis.
- At least one of the two opposite edges of at least one of the damping strips is shaped such that liquid present in this edge can flow by gravity towards either or both of its upstream and downstream ends.
- the invention thus provides a simple and high performance solution capable of discharging liquids towards either or both ends of the edges likely to be wetted by such liquids, as oil or kerosene.
- the fluids can flow onto the fan casing down to the low part of the same, or at which they are preferentially discharged by a drain located at 6 o'clock on the casing.
- damping strips are therefore non longer likely to be degraded by the prolonged retention of liquids on their edges, which enables a high performance damping function to be preserved for a long time.
- the arrangement specific to the present invention is provided on each edge of each strip likely to collect fluid dripping by gravity on the lower surface of the casing, that is generally a single edge per band, this being oriented upwards.
- At least one of both opposite edges of at least one of the damping strips has at least one portion tilted with respect to the center axis, such that liquid present on this portion can flow by gravity towards either or both of its upstream and downstream ends.
- the tilted portion is preferentially planar, but can alternatively be curved.
- Each edge concerned can include here only a single tilted portion, preferably making up the entire edge.
- At least one of the two opposed edges of at least one of the damping strips consists of two successive portions in the direction of the center axis, each of both portions being tilted along the center axis such that liquid present on each of both portions can flow by gravity towards the upstream end and the downstream end respectively.
- This enables the liquid to be distributed towards both upstream and downstream ends of the edge concerned, and a possible liquid overflow at one of its ends, and a spilling into the jet.
- the two tilted portions arranged as downwardly open V, can be symmetrical.
- the angle formed between both edge portions is preferably between 1 and 15°, and more preferably between 1 and 3°.
- both edge portions are at the same length, and symmetrically arranged.
- At least one of the damping strips is shaped so as to be mountable onto the acoustic panel at two reversed mounting positions, wherein the positions of said two opposite edges are respectively reversed, and in that in each of both mounting positions, at least one the two opposite edges of said damping strip is shaped such that liquid present on this edge can flow by gravity towards either or both of its upstream and downstream ends.
- At least one of the damping strips has a first plan of symmetry arranged between the two opposite edges.
- all the strips have an identical shape, which still further simplifies the mounting.
- At least one of the damping strips has a second plan of symmetry passing through both opposite edges, said first and second plans of symmetry being preferentially orthogonal between them, and also orthogonal to the strip plan when the same has a substantially planar surface.
- each damping strip is preferably made of an elastomeric material.
- An other object of the invention is also to provide an aircraft turbomachine front part comprising a fan casing the internal surface of which is coated with at least one acoustic protection device such as described above.
- FIG. 1 shows a perspective view of an aircraft turbojet engine fan casing, equipped with an acoustic protection device according to a preferred embodiment of the invention
- FIG. 2 represents a perspective view of the acoustic protection device shown in the preceding figure, at an angle enabling its internal surface to be seen;
- FIGS. 3 and 4 respectively represent cross section views taken along lines III-III and IV-IV of FIG. 2 , respectively;
- FIG. 5 represents a perspective view of one of the vibration damping strips equipping the acoustic protection device shown in the preceding figures;
- FIG. 6 represents a side view of an acoustic protection device part shown in the preceding figures.
- FIG. 7 represents a view similar to that of the preceding view, according to an alternative embodiment.
- a fan casing 1 intended to be an integral part of a front part of an aircraft turbojet engine, preferably of the two flow twin-spool type.
- the casing assumes a conventional ferrule shape, with a longitudinal axis 2 corresponding to the longitudinal axis of the turbojet engine assembly.
- the internal surface 1 a of the casing 1 a is equipped with a plurality of acoustic protection devices 4 , only one of which has been represented in FIG. 1 .
- This device 4 includes an acoustic protection panel 6 forming a ferrule sector centered on a center axis the same as the longitudinal axis 4 .
- the panel 6 is preferentially assembled by screwing on the casing, the fixing screws 8 being mounted hidden in the panel so as not to disturb the streamline flow of the jet.
- the device 2 also comprises one or more vibration damping strips 10 pressed on one side to the external surface 6 a of the panel 6 , and for being pressed on the other side to the internal surface 1 a of the casing 1 .
- each strip 10 spaced apart from each other along the circumferential direction, are made of elastomeric material. They are generally oriented parallel to the axis 2 , that is they have their length parallel to this axis, and their width orthogonal to the same axis 2 . In the preferred embodiment represented, each strip 10 has a low width, enabling it to preserve a substantially planar shape, but it could alternatively be curved, without departing from the scope of the invention.
- FIG. 3 shows the panel 6 assembled on the casing 1 by the screws 8
- FIG. 4 shows the interposition of one of the damping strips 10 between both surfaces 1 a , 6 a between which this strip is compressed in order to provide its vibration damping function.
- FIGS. 5 and 6 more precisely show one of the strips 10 , as well as its arrangement on the casing.
- all the strips 10 of the device 4 are provided to be identical.
- the strip 10 has a first plan of symmetry 12 orthogonal to the axis 2 , and corresponding to a median plan passing between the two longest opposite edges, called longitudinal edges 4 .
- the strip 10 has also a second plan of symmetry 16 orthogonal to the first plan 12 , and corresponding to a median plan passing between the shortest two opposite edges, called transverse edges 18 .
- Both plans 12 , 16 are orthogonal to the plan of the strip 10 , the transverse edges 18 of which are parallel to the first plan 12 . Consequently, in a side view as shown in FIG. 6 , the edges 18 are considered as vertical edges.
- each longitudinal edge 14 extends between an upstream end and a downstream end spaced from each other along the direction of the center axis 2 , by consisting of two successive portions 14 a , 14 b in the direction of the same axis 2 , tilted with respect to each other, and each substantially planar. Both portions of the longitudinal edge 14 a , 14 b , of a substantially identical length, form an angle preferably between 1 and 3°.
- the damping strip 10 is shaped so as to be mountable to the panel 6 at two reversed mounting positions, wherein the positions of both opposite longitudinal edges 14 are respectively reversed, that is that in one of both positions, one of the edges is usually oriented upwards, whereas it is oriented downwards in the other position. Because of the symmetry of the strip 10 along the first plan 14 , regardless of the mounting direction adapted, the strip has a same configuration on the panel 6 . Therefore, a mounting mistake can not happen, since in both mounting directions, the longitudinal edge 14 likely to collect liquid leaks, that is the one oriented upwards, will be able to lead liquids by gravity up to both ends of this edge, to provide discharge thereof.
- each of the two edge portions 14 a , 14 b can lead by gravity a collected liquid, for example an oil and/or kerosene leak, to the edge end it integrates.
- a collected liquid for example an oil and/or kerosene leak
- the liquid can then flow between both surfaces 1 a , 6 a down to the low part of the blower casing, to be then discharged through a drain (not shown) located at 6 o'clock at the casing 1 .
- Each upwardly oriented edge 14 is related to a facet/rim enabling, by virtue of its tilting(s) with respect to the horizontal direction, discharge of liquid leaks remote from the damping strips 10 .
- FIG. 7 shows an alternative to make the strips 10 , each herein taking a generally parallelogram shape with each longitudinal edge 14 consisting of a single portion tilted with respect to the center axis 2 , so as to form a slope dedicated to the pouring of the liquid to one of the edge ends, herein the downstream end.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Vibration Prevention Devices (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
Description
Claims (10)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1161819A FR2984429B1 (en) | 2011-12-16 | 2011-12-16 | VIBRATION DAMPING BANDS WITH FLUID EXHAUST, FOR ACOUSTIC PROTECTION OF AIRCRAFT TURBOMACHINE BLOWER HOUSING |
FR1161819 | 2011-12-16 | ||
PCT/FR2012/052938 WO2013088088A1 (en) | 2011-12-16 | 2012-12-14 | Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing |
Publications (2)
Publication Number | Publication Date |
---|---|
US20140369816A1 US20140369816A1 (en) | 2014-12-18 |
US9631640B2 true US9631640B2 (en) | 2017-04-25 |
Family
ID=47559556
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/363,898 Active 2034-05-26 US9631640B2 (en) | 2011-12-16 | 2012-12-14 | Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing |
Country Status (9)
Country | Link |
---|---|
US (1) | US9631640B2 (en) |
EP (1) | EP2800906B1 (en) |
JP (1) | JP6042905B2 (en) |
CN (1) | CN103998791B (en) |
BR (1) | BR112014014436B1 (en) |
CA (1) | CA2858165C (en) |
FR (1) | FR2984429B1 (en) |
RU (1) | RU2607688C2 (en) |
WO (1) | WO2013088088A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2940251B1 (en) | 2014-04-28 | 2019-06-12 | Rolls-Royce Corporation | Fan containment case |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3542152A (en) | 1968-04-08 | 1970-11-24 | Gen Electric | Sound suppression panel |
US4293053A (en) * | 1979-12-18 | 1981-10-06 | United Technologies Corporation | Sound absorbing structure |
US4751979A (en) | 1985-05-16 | 1988-06-21 | Airborne Express, Inc. | Engine noise suppression kit for the nacelles of a jet aircraft |
US4926963A (en) | 1987-10-06 | 1990-05-22 | Uas Support, Inc. | Sound attenuating laminate for jet aircraft engines |
US20060219475A1 (en) | 2005-03-30 | 2006-10-05 | Olsen Ronald F | Flow restrictors for aircraft inlet acoustic treatments, and associated systems and methods |
US20090321178A1 (en) * | 2008-06-30 | 2009-12-31 | Durchholz Anthony J | Method and system for damped acoustic panels |
WO2010109152A2 (en) | 2009-03-27 | 2010-09-30 | Airbus Operations Sas | Aircraft nacelle comprising a reinforced outer wall |
US20120107125A1 (en) | 2009-04-29 | 2012-05-03 | Snecma | Reinforced fan blade shim |
US20120138950A1 (en) | 2009-08-04 | 2012-06-07 | Gan Systems Inc. | Island matrixed gallium nitride microwave and power switching transistors |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
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US4384634A (en) * | 1979-12-18 | 1983-05-24 | United Technologies Corporation | Sound absorbing structure |
JPS639401U (en) * | 1986-07-04 | 1988-01-22 | ||
FR2752392B1 (en) * | 1996-08-14 | 1999-04-23 | Hispano Suiza Sa | VENTILATED HONEYCOMB SANDWICH PANEL AND VENTILATION METHOD FOR SUCH A PANEL |
DE69722345T2 (en) * | 1996-10-21 | 2004-02-26 | United Technologies Corp. (N.D.Ges.D. Staates Delaware), Hartford | Guide grille for the flow path of a gas turbine |
US6637186B1 (en) * | 1997-11-11 | 2003-10-28 | United Technologies Corporation | Fan case liner |
RU2148732C1 (en) * | 1998-05-05 | 2000-05-10 | Открытое акционерное общество Самарский научно-технический комплекс им. Н.Д. Кузнецова | Turbo-machine stage |
US7018172B2 (en) * | 2003-12-22 | 2006-03-28 | United Technologies Corporation | Airfoil surface impedance modification for noise reduction in turbofan engines |
US7866440B2 (en) * | 2006-07-21 | 2011-01-11 | Rohr, Inc. | System for joining acoustic cellular panel sections in edge-to-edge relation |
FR2908737B1 (en) * | 2006-11-16 | 2009-12-04 | Airbus France | ACOUSTIC COATING FOR AIRCRAFT INCORPORATING A JELLY EFFECT FROST TREATMENT SYSTEM. |
FR2912780B1 (en) * | 2007-02-20 | 2012-03-02 | Airbus France | COATING FOR ACOUSTIC TREATMENT INCORPORATING AN ALVEOLAR STRUCTURE WITH A COMPLEX SHAPE |
-
2011
- 2011-12-16 FR FR1161819A patent/FR2984429B1/en active Active
-
2012
- 2012-12-14 US US14/363,898 patent/US9631640B2/en active Active
- 2012-12-14 CN CN201280060814.3A patent/CN103998791B/en active Active
- 2012-12-14 CA CA2858165A patent/CA2858165C/en active Active
- 2012-12-14 BR BR112014014436-2A patent/BR112014014436B1/en active IP Right Grant
- 2012-12-14 RU RU2014129011A patent/RU2607688C2/en active
- 2012-12-14 JP JP2014546618A patent/JP6042905B2/en active Active
- 2012-12-14 WO PCT/FR2012/052938 patent/WO2013088088A1/en active Application Filing
- 2012-12-14 EP EP12815744.3A patent/EP2800906B1/en active Active
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3542152A (en) | 1968-04-08 | 1970-11-24 | Gen Electric | Sound suppression panel |
US4293053A (en) * | 1979-12-18 | 1981-10-06 | United Technologies Corporation | Sound absorbing structure |
US4751979A (en) | 1985-05-16 | 1988-06-21 | Airborne Express, Inc. | Engine noise suppression kit for the nacelles of a jet aircraft |
US4926963A (en) | 1987-10-06 | 1990-05-22 | Uas Support, Inc. | Sound attenuating laminate for jet aircraft engines |
US20060219475A1 (en) | 2005-03-30 | 2006-10-05 | Olsen Ronald F | Flow restrictors for aircraft inlet acoustic treatments, and associated systems and methods |
US20090321178A1 (en) * | 2008-06-30 | 2009-12-31 | Durchholz Anthony J | Method and system for damped acoustic panels |
WO2010109152A2 (en) | 2009-03-27 | 2010-09-30 | Airbus Operations Sas | Aircraft nacelle comprising a reinforced outer wall |
US20120060938A1 (en) | 2009-03-27 | 2012-03-15 | Airbus Operations Sas | Aircraft nacelle comprising a reinforced outer wall |
US20120107125A1 (en) | 2009-04-29 | 2012-05-03 | Snecma | Reinforced fan blade shim |
US20120138950A1 (en) | 2009-08-04 | 2012-06-07 | Gan Systems Inc. | Island matrixed gallium nitride microwave and power switching transistors |
Non-Patent Citations (1)
Title |
---|
International Search Report Issued May 17, 2013 in PCT/FR12/052938 Filed Dec. 14, 2012. |
Also Published As
Publication number | Publication date |
---|---|
FR2984429A1 (en) | 2013-06-21 |
BR112014014436A2 (en) | 2017-06-13 |
EP2800906A1 (en) | 2014-11-12 |
CN103998791B (en) | 2016-08-17 |
JP6042905B2 (en) | 2016-12-14 |
CN103998791A (en) | 2014-08-20 |
RU2014129011A (en) | 2016-02-10 |
RU2607688C2 (en) | 2017-01-10 |
FR2984429B1 (en) | 2014-02-14 |
US20140369816A1 (en) | 2014-12-18 |
JP2015505933A (en) | 2015-02-26 |
CA2858165A1 (en) | 2013-06-20 |
CA2858165C (en) | 2019-07-02 |
BR112014014436B1 (en) | 2021-03-16 |
EP2800906B1 (en) | 2016-05-25 |
WO2013088088A1 (en) | 2013-06-20 |
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